TY - JOUR
T1 - Teardrop hovering formation for elliptical orbit considering J2 perturbation
AU - Bai, Shengzhou
AU - Han, Chao
AU - Sun, Xiucong
AU - Zhang, Hongli
AU - Jiang, Yiping
N1 - Funding Information:
This research was supported by National Natural Science Foundation of China (No. 11902012 ), Space Science and Technology Fund and Academic Excellence Foundation of BUAA for PHD Students . We thank LetPub ( www.letpub.com ) for its linguistic assistance during the preparation of this manuscript.
Publisher Copyright:
© 2020 Elsevier Masson SAS
Copyright:
Copyright 2020 Elsevier B.V., All rights reserved.
PY - 2020/11
Y1 - 2020/11
N2 - On-orbit service (OOS) technologies, applied to provide essential maintenance to prolong the lifetime of spacecraft and to extend their function, have received widespread attention recently. The hovering formation, as one of the core technologies, enables the relative motion state between an active spacecraft and chief spacecraft within a specified range. In this study, we proposed a teardrop hovering formation, which is suitable for elliptical reference orbit with a J2 perturbation. We formulated a mathematical model of the teardrop hovering formation maintained by the impulse control and presented a rapid method based on the state transition matrix. With the triangles of the three tangent lines solved by the rapid method, we estimated the envelope of the multi-loop hovering formation. Furthermore, we analyzed the influence of the reference orbital elements and formation parameters on the hovering formation by numerical simulations, which demonstrated the efficiency of the proposed method and provided a reference for the preliminary design of hovering formations.
AB - On-orbit service (OOS) technologies, applied to provide essential maintenance to prolong the lifetime of spacecraft and to extend their function, have received widespread attention recently. The hovering formation, as one of the core technologies, enables the relative motion state between an active spacecraft and chief spacecraft within a specified range. In this study, we proposed a teardrop hovering formation, which is suitable for elliptical reference orbit with a J2 perturbation. We formulated a mathematical model of the teardrop hovering formation maintained by the impulse control and presented a rapid method based on the state transition matrix. With the triangles of the three tangent lines solved by the rapid method, we estimated the envelope of the multi-loop hovering formation. Furthermore, we analyzed the influence of the reference orbital elements and formation parameters on the hovering formation by numerical simulations, which demonstrated the efficiency of the proposed method and provided a reference for the preliminary design of hovering formations.
KW - Elliptical reference
KW - Hovering formation
KW - On-orbit service
KW - Preliminary design
KW - State transition matrix
UR - http://www.scopus.com/inward/record.url?scp=85089469253&partnerID=8YFLogxK
U2 - 10.1016/j.ast.2020.106098
DO - 10.1016/j.ast.2020.106098
M3 - Journal article
AN - SCOPUS:85089469253
SN - 1270-9638
VL - 106
JO - Aerospace Science and Technology
JF - Aerospace Science and Technology
M1 - 106098
ER -